AirplaneDesign.aero

Guest

For anyone looking for a good airfoil analysis tool, XFOIL is the place to start. Plus, its free!

It does take a little getting used to, especially if you're looking for a tool with a graphical user interface (GUI). XFOIL is primarily text driven, but is very straight forward, and comes with a good manual.

You can download the software at the site below.
http://raphael.mit.edu/xfoil/

There is also a Yahoo! Group dedicated to XFOIL users, which is highly active with dozens of members. If you have a question about XFOIL, that is the place to go.

The XFOIL Yahoo! Group is located at:
http://groups.yahoo.com/group/xfoil/

MarBucz · Newbie Joined: 17 Jun 2004 Posts: 7

there is a program called Profili, which use the Xfoil. You can find information on this link
www.profili2.com

Guest · Posted: Mon Jun 28, 2004 7:30 am Post subject:

Hi MarBucz,

Good reference! Do you have any experience with Profili? Do they have comparison data with wind tunnel data?

MarBucz · Newbie Joined: 17 Jun 2004 Posts: 7

We are using Profili in our firm to compare different airfoils. we try to improve configuration of our airplane JK-05 (which you can see on photos).
There are two version of this program: standart and a new one Profi. Most important difference is in range of angle of attack to calculate. I don't know about comparison with wind tunnel data, but it looks the results from Profili are good. Profili has problems with some configuration of airfoils for example airfoil with "crocodile" flap, so for this configuration you should use an CFD programs. Generally it is very good prog and not expensive (~50 EURO).

Guest · Posted: Tue Jun 29, 2004 11:42 am Post subject:

Very interesting. Will it calculate what happens in the non-linear range of angle of attack?

MarBucz · Newbie Joined: 17 Jun 2004 Posts: 7

In one word: YES. The profi version calculate the whole range of angle attack: negative and positive. The standart version has the limit from -8 to +13 degrees.

ArrowHawk · Newbie Joined: 12 Sep 2004 Posts: 4

The profili program uses X-Foil to calculate the aerodynamic characteristics of airfoils. I have version 2.15 which has an alpha range of -8 to 13 degrees. Planning on getting the Pro version which gives you a full range of alphas. Version 2.15 was $12 and Pro will probably be about $20.

ArrowHawk

gregoryp · Newbie Joined: 07 Sep 2004 Posts: 2

Any chance someone can post some CL/AoA results for say Clark YH at a 9,000,000 reynolds number range?

I've used a couple programs and all seem to have a problem with this airfoil.

JavaFoil seems to work ok but has problems with airfoils greater than 12%
http://www.mh-aerotools.de/airfoils/javafoil.htm

kmichael · Newbie Joined: 27 Dec 2005 Posts: 8

I don't know if this would close enough to what you are looking for, but Handbook of Airfoil Sections for Light Aircraft by M.S. Rice has data for the Clark Y, Clark YM-15 and Clark YM-18 at around R = 3,100,000.
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